Last edited by Dougar
Wednesday, August 12, 2020 | History

2 edition of Evaluation of turbulance reduction devices for the Langley 8-Foot Transonic Pressure Tunnel found in the catalog.

Evaluation of turbulance reduction devices for the Langley 8-Foot Transonic Pressure Tunnel

Marion O McKinney

Evaluation of turbulance reduction devices for the Langley 8-Foot Transonic Pressure Tunnel

by Marion O McKinney

  • 388 Want to read
  • 25 Currently reading

Published by National Aeronautics and Space Administration, Scientific and Technical Information Branch, For sale by the National Technical Information Service in Washington, D.C, [Springfield, Va .
Written in English

    Subjects:
  • Transonic wind tunnels,
  • Laminar flow

  • Edition Notes

    StatementMarion O. McKinney and James Scheiman
    SeriesNASA technical memorandum -- 81792
    ContributionsScheiman, James, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
    The Physical Object
    Pagination30 p. :
    Number of Pages30
    ID Numbers
    Open LibraryOL14925678M


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Evaluation of turbulance reduction devices for the Langley 8-Foot Transonic Pressure Tunnel by Marion O McKinney Download PDF EPUB FB2

Evaluation of turbulance reduction devices for the Langley 8-Foot Transonic Pressure Tunnel. Washington, D.C.: National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.: For sale by the National Technical Information Service, ] (OCoLC) Material Type.

Buy Evaluation of turbulance reduction devices for the Langley 8-Foot Transonic Pressure Tunnel (NASA technical memorandum) by Marion O McKinney (ISBN:) from Amazon's Book Store. Everyday low prices and free delivery on eligible : Marion O McKinney. The NASA Langley 8-Foot Transonic Pressure Tunnel (8-Foot TPT) is a continuous-flow, variable-pressure wind tunnel with control capability to inde-pendently vary Mach nmnber, stagnation pressure, stagnation temperature, and humidity.

The test sec-tion is square with corner fillets and a cross-sectional area approximately equivalent to that of.

McKinney, Marion O.; and Scheiman, James: Evaluation of Turbulence Reduction Devices for the Langley 8-Foot Transonic Pressure Tunnel NASA TM, Google Scholar [18]Cited by: 3. The NASA Langley 8-Foot High Temperature Tunnel (8-Ft. HTT) is a combustion-heated hypersonic blowdown-to-atmosphere wind tunnel that provides flight simulation over a Mach number range from 4 to 7 and an altitude range f tofeet.

The facility is used for both air-breathing propulsion testing and aero-Cited by: 6. Two-dimensional aerodynamic characteristics of the NACA airfoil in the Langley 8 foot transonic pressure tunnel by Harris, C.

Full text of "Two-dimensional aerodynamic characteristics of the NACA airfoil in the Langley 8 foot transonic pressure tunnel" See other formats Nei 1^ m m 13 2 Li Z 1^ iZO il.4 il.6 NASA Technical Memorandum {NASA-TM) TWO-DIMENSIOHAL AERODYKAMIC CHARACTERISTICS OF THE NACA AIBFOIL IN THE LANGLEY 8 FOOT TfiANSOHIC.

Turbulence. See also what's at Wikipedia, your library, or elsewhere. Broader term: Fluid dynamics; Narrower terms: Turbulence -- Mathematical models; Aerodynamic noise; Atmospheric turbulence. The Eight-Foot High Speed Tunnel is a single-return atmospheric pressure tunnel with an 8-foot diameter closed-throat test section.

The tunnel became operational in and at that time had a maximum speed of Mach driven by an 8,horsepower electric motor/fan. Foot Transonic Tunnel. The Langley Foot Transonic Tunnel (Ft TT) is an atmospheric, closed-circuit tunnel with a Mach number range of to and a Reynolds number range from 1 x 10 6 to 4 x 10 6 per foot.

The test section of the tunnel is octagonal with a distance of ft across the flats. The last major wind tunnel accident at NASA Langley occurred inwhen a chunk of metal broke from a piece of machinery and destroyed fan blades in the Foot Transonic Tunnel. That book A Helping Of Love comes in PDF format or other Evaluation of turbulance reduction devices for the langley 8 foot transonic pressure tunnel Eestimaa rekordid Grain refining heat treatments to improve cryogenic toughness of high strength steels.

Guide to NACA Historical Sources at Langley [] Since this book is amply footnoted by chapter, and since so little is generally known about the recently constituted archives that provided most of my source material, I have chosen to provide readers with the following general-purpose guide to the major sources for research into NACA history at NASA Langley Research Center instead of with the.

Langley Research Center: Basic pressure measurements on a scale model of the North American X research airplane at transonic speeds / (Washington [D.C.]: National Aeronautics and Space Administration, []), also by Robert S. Osborne, Virginia C.

Stafford, and United States National Aeronautics and Space Administration (page images. Compressibility effects in the shear layer over a rectangular cavity. SciTech Connect.

Beresh, Steven J.; Wagner, Justin L.; Casper, Katya M. we studied the influence. Experiments on two- and three-dimensional vortex flows in lid-driven cavities. NASA Astrophysics Data System (ADS) Siegmann-Hegerfeld, Tanja; Albensoeder, Stefan; Kuhlmann, Hendri.